Abstract
The pre-selected landing point of Chang’E-4 probe lies in von Karman Crater on the farside of the Moon. Because the available landing zone is very small, the probe needs several orbit maneuvers for pinpoint and punctual landing. In view of this problem, a method base on analytic solution and simple iteration is put forward. Firstly, the relationship between landing point and the lunar-descent-phase initial point is analyzed, and corresponding conversion formula is given. Secondly, the relationship between longitude deviation of landing point and deviation of orbit plane is analyzed. Thirdly, a set of proper orbit control strategies of the probe are proposed and discussed, including translation methods from deviation of orbit plane to yaw angle of maneuver and adaptation methods from landing time to semi-major axis according to different flying phases. Finally, the application of the proposed strategies and algorithms of orbit control in Chang’E-4 mission is introduced, and the feasibility and validity are illustrated by the actual results.
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